CN115071996A

CN115071996A - Three-piece safety guarantee clamp

Info

Publication number: CN115071996A
Application number: CN202210247990.3A
Authority: CN
Inventors: A·斯米尔; K·蔡
Original assignee: Boeing Co
Current assignee: Boeing Co
Priority date: 2021-03-16
Filing date: 2022-03-14
Publication date: 2022-09-20
Also published as: EP4059835A1; EP4059835B1; CA3152022A1; US11933353B2; US20220299063A1; JP2022142775A

Abstract

The application relates to a three-piece safety guarantee clamp. The three-piece safety assurance clamp includes a central portion having a central top surface, a planar first outer surface, and a planar second outer surface. The second outer surface is oriented opposite the first outer surface. A channel in the central portion is configured to receive the tension and compression member. The left side portion is connected adjacent the first outer surface. The left side portion has a flat first inner surface received against the first outer surface and a left top surface coplanar with the central top surface. The right side portion is connected adjacent the second outer surface. The right side portion has a flat second inner surface received against the second outer surface and a right top surface coplanar with the central top surface.

Description

Three-piece safety guarantee clamp

Technical Field

The present disclosure relates generally to the field of aircraft deployment systems having an under-wing support with a three-piece safety assurance clamp.

Background

Aircraft employ deployment systems to articulate surfaces. For example, commercial aircraft have flaps that are deployed to increase the camber and chord of the wing for enhanced performance at takeoff and landing. Various mechanical devices have been developed to deploy flaps from a retracted position to an extended position. The flap support typically extends below the lower surface of the wing, and the deployment of the flap extends portions of the flap and the flap support element below the wing. The main structural elements (PSE) in the flap support element comply with safety and safety requirements. This may mean a "back-to-back" replication of the sections of the structure that are primarily under tension. For the lug this is a relatively simple addition to the design, but for the clamp it becomes more complex, expensive and difficult to build.

An example of a safety and security clip for the under-wing support fitting as shown in figures 1A to 1C, consisting of a main outer part 2 and an inner nesting part 4 of the fitting 3, can be found on existing commercial aircraft. This structure requires that the interface between these inner and outer parts comprises three surfaces that are orthogonal to each other. For machined parts, this requires tighter tolerances, which are expensive to meet and result in higher scrap rates, and requires shimming of the design in the gap. In addition, the fastener 5 common to both parts of the fitting and mating part 6 must penetrate a thicker stack than the fastener 7 that penetrates only the outer part, preventing the use of a single clamping length without other structural adaptations. The varying clamping length makes assembly more complex, slower and more expensive.

It is therefore desirable to provide an under-wing support that overcomes these disadvantages of the prior art.

Disclosure of Invention

An exemplary implementation of a three-piece safety assurance clamp includes a central portion having a central top surface, a planar first outer surface, and a planar second outer surface. The second outer surface is oriented opposite the first outer surface. A channel in the central portion is configured to receive the tension and compression member. The left side portion is connected adjacent the first outer surface. The left side portion has a flat first inner surface received against the first outer surface and a left top surface coplanar with the central top surface. The right side portion is connected adjacent the second outer surface. The right side portion has a flat second inner surface received against the second outer surface and a right top surface coplanar with the central top surface.

Exemplary implementations provide a method for engaging tension and compression members with a three-piece safety assurance clamp. A central portion having a central top surface is received on the lower surface of the wing, the central portion having a left inner flange and a left inner tang having a first planar outer surface and a right inner flange and a left inner tang having a second planar outer surface that is oppositely oriented from the first outer surface. A left side portion is connected with the left outer flange and the left outer tang adjacent the first outer face using a first plurality of field fasteners, the left side portion having a flat first inner face received against the first outer face and a left top face coplanar with the central top face and received on the lower face. A right side portion having a flat first inner surface received against the first outer surface and a right top surface coplanar with the central top surface and received on the lower surface is connected with the right outer flange and the right outer tang adjacent the second outer surface using a second plurality of field fasteners. The tension and compression member is received in a channel between the left inner tang and the right inner tang in the central portion.

Drawings

The features, functions, and advantages that have been discussed can be achieved independently in various implementations or may be combined in yet other implementations further details of which can be seen with reference to the following description and drawings.

FIG. 1A is a rear perspective view of a prior art under-wing support fitting;

FIG. 1B is a rear view of the prior art under-wing support fitting of FIG. 1A;

FIG. 1C is an exploded view of the components of the under-wing support fitting of FIG. 1A;

FIG. 2A is a representation of an aircraft in which implementations disclosed herein may be employed;

FIG. 2B is a top view of the wing and flaps of the aircraft of FIG. 2A;

FIG. 2C is a side detailed view of a flap structure incorporating an under-wing support fitting that may employ the disclosed implementations (with the fairing removed);

FIG. 3A is a rear perspective view of a three-piece safety assurance clamp for a under-wing support fitting;

FIG. 3B is a rear view of the three-piece safety assurance clamp of FIG. 3A;

FIG. 3C is a bottom view of the three-piece safety assurance clamp of FIG. 3A;

FIG. 3D is a side view of the three-piece safety assurance clamp of FIG. 3A;

FIG. 3E is a left rear exploded view of the components of the three-piece safety assurance clamp of FIG. 3A;

FIG. 3F is a rear right exploded view of the components of the three-piece safety assurance clamp of FIG. 3A;

FIG. 3G is a rear perspective view showing an alternative configuration of a clamp for single pin engagement;

FIG. 4A is a perspective view of a first safety and security condition with a crack in one of the external components of an example implementation;

FIG. 4B is a side view of a first safety condition;

FIG. 5 is a perspective view of a second safety condition with a crack in a central component of an example implementation; and

FIG. 6 is a flow chart of a method for engaging tension and compression members with a three-piece safety assurance clamp.

Detailed description of the invention

Implementations described herein provide an under-wing support with a three-piece safety assurance clamp that incorporates three laterally adjacent components, which simplifies the assembly process and reduces or eliminates the need to include design clearances that may require shimming. The common flange thickness in all three laterally adjacent components allows for the use of a single common clamp length fastener. The three-piece safety guarantee clamp maintains necessary structural performance characteristics and meets safety guarantee requirements.

Although implementations are described herein with reference to an underwing support structure for a flap system, implementations may be applicable to any Primary Structural Element (PSE).

Referring to the drawings, fig. 2A, 2B and 2C show an aircraft 10 having a wing 12 with a system for operating flaps 14. The flap 14 is joined to the wing 12 at a plurality of attachment points, with flap supports 15a, 15B at least partially housed within the fixed and movable fairings 16A, 16B. The flaps 14 are deployed to enhance aerodynamic performance during take-off and landing with flap actuation mechanisms 18 that cause the flaps 14 and movable fairing 16b to rotate aft and downward relative to the wing 12.

With the

fairings

16a, 16b removed, as shown in fig. 2C, the flap supports 15a, 15b extending from the structure of the wing 12 each incorporate an under-wing fitting that employs a three-piece safety clip 20, as will be described in more detail subsequently. In the example shown, the rotary actuator 22 is supported between a pair of flap support ribs 23 (the outboard flap support ribs removed for clarity), with drive arms 24 extending radially from the actuator for rotation upon actuation of the actuator. The flap support rib 23 is connected to the rear spar 25, which is adjacent to the upper flange 27. The coupling link 26 is pivotally attached at a forward end to the drive arm 24 with a pivot pin 29, whereby rotation of the actuator rotates the drive arm 24 to extend the coupling link 26.

A spherical bearing or similar engagement element may be used in the forward end of the coupling link 26 to accommodate angular alignment. The flap 14 is mounted on a load beam 30 and is rotatably coupled to the wing 12 by a flap support rib 23. The load beam 30 is rotatably attached at a lower apex 34 to a rear clamp 36 formed by the inboard and outboard ribs 23 with an axle 32. The connecting link 26 extends from the drive arm 24 to the load beam 30 and is pivotally attached to the load beam with a second pivot pin 33.

In the example shown, the three-piece safety assurance clamp 20 attached to the lower surface 35 of the wing 12 provides tension support at the aft clamp 36 with tension and compression members 37 or other structural links connected to the aft clamp 36 with pins 38. The tension and compression members 37 are engaged with the

frangible pins

39a and 39b by the safety clip 20 to achieve ground contact safety.

Fig. 3A to 3E show an example implementation of the three-piece safety assurance clamp 20. The three-piece safety assurance clamp 20 has a central portion 102 with a central top flange 104. The body portion 106 has a left inner flange 108a and a right inner flange 108b depending perpendicularly from the central top flange 104. A left inner tang 110A extends rearwardly from the left inner flange 108a and a right inner tang 110b extends rearwardly from the right inner flange 108 b. The left inner flange 108a and the left inner tang 110a have a flat first outer surface 112, while the right inner flange 108b and the right inner tang 110b have a flat second outer surface 114 that is parallel and oppositely oriented to the first outer surface 112. The right inner surface 116a of the left inner tang 110a and the left inner surface 116b of the right inner tang 110b ride over a channel 118 configured to receive the tension and compression member 37.

The left side portion 202 is connected adjacent a first outer surface 112 of the center portion 102, while the right side portion 302 is connected adjacent a second outer surface 114 of the center portion 102 opposite the left side portion 202. The left side portion 202 has a left top flange 204. A left outer flange 206 depends perpendicularly from the left top flange 204, and a left outer tang 208 extends rearwardly from the left outer flange 206. The left outer flange 206 and the left outer tang 208 together form a flat first inner surface 209. The first inner surface 209 of the left side portion 202 is received against the first outer surface 112 of the central portion 102.

The right side portion 302 has a right top flange 304. A right outer flange 306 depends perpendicularly from the right top flange 304 and a right outer tang 308 extends rearwardly from the left outer flange 206. The right outer flange 306 and the right outer tang 308 together form a flat second inner surface 309. The second inner surface 309 of the right side portion 302 is received against the second outer surface 114 of the center portion 102.

The left top surface 210 of the left top flange 204 and the right top surface 310 of the right top flange 304 are coplanar with the center top surface 111 of the center top flange 104. This provides a single flat top surface 113 for the three-piece safety clip 20. The central top flange 104 has a first plurality of apertures 120 configured to receive a first plurality of fasteners 122 a. The left top flange 204 has a plurality of holes 220 to receive the second plurality of fasteners 122b and the right top flange 304 has a third plurality of holes 320 to receive the third plurality of fasteners 122 c. The first thickness 130 of the center top flange 104, the second thickness 230 of the left top flange 204, and the third thickness 330 of the right top flange 304 are equal. This allows the first, second, and third pluralities of

fasteners

122a, 122b, and 122c to have equal clip lengths 123 for attachment to the under wing skin.

The left side portion 202 is secured to the center portion 102 using a first plurality of field fasteners 124, while the right side portion 302 is secured to the center portion 102 using a second plurality of field fasteners 126.

The first array of apertures 128a in the left inner flange 108a is concentrically aligned with the first array of mating apertures 228a in the left outer flange 206. Similarly, the second array of apertures 128b in the right inner flange 108b is concentrically aligned with the second array of mating apertures 328b in the right outer flange 306.

The third array of holes 129a in the left inner tang 110a is concentrically aligned with the third array of mating holes 229a in the left outer tang 208. Similarly, the fourth array of holes 129b in the inner right tang 110b is concentrically aligned with the fourth array of mating holes 329b in the outer right tang 308.

First hole array 128a, first mating hole array 228a, third hole array 129a, and third mating hole array 229a receive first plurality of field fasteners 124. Similarly, second aperture array 128b, second mating aperture array 328b, fourth aperture array 129b, and fourth mating aperture array 329b receive a second plurality of field fasteners 126.

In the example implementation for engagement of the

frangible pins

39a, 39b, the first pair of receiving

holes

140a and 140b in the first and second

inner tangs

110a, 110b are concentrically aligned with the first mating receiving hole 240 in the left outer tang 208 and the second mating receiving hole 340 in the right outer tang 308, and the second pair of receiving holes 142a and 142b are concentrically aligned with the third mating receiving hole 242 in the left outer tang 208 and the fourth mating receiving hole 342 in the right outer tang 308. In an alternative implementation as shown in fig. 3G, a single pair of receiving

holes

150a and 150b in the first and second

inner tangs

110a and 110b concentrically aligned with the first and second

mating receiving holes

250 and 350 in the left and right

outer tangs

208 and 308 may be used for single pin engagement.

As shown in fig. 4A and 4B, the geometric arrangement of first, second, third, and fourth

mating hole arrays

228a, 328a, 229a, and 329B is configured to surround a potential propagating crack in either left or right

outer rims

206, 306 or left or right

outer tangs

208, 308 for transmission or loading by respective field fasteners to either left or right inner rims 108a, 108B or left or right inner tangs 110a, 110B. An example crack 400 is shown in the left outer flange and the left outer tang.

Similarly, as shown in fig. 5, the geometric arrangement of first, second, third, and

fourth hole arrays

128a, 128b, 129a, 129b is configured to surround a potential propagating crack in either the left or right

inner flange

108a, 108b or the left or right

inner tang

110a, 110b for transmission or loading by respective field fasteners to the left or right

outer flange

206, 306 or the left or right

outer tang

208, 308.

The engagement of the planar first inner surface 209 with the first outer surface 112 and the engagement of the second inner surface 309 with the second outer surface 114 provide very high tolerance engagement of the center portion 102, left side portion 202, and right side portion 302 limited only by machining tolerances of the planar surfaces. Similarly, during installation of the field fastener, very high tolerances are maintained in the flat top surface 113 with the engagement of the center top surface 111, the left top surface 210, and the right top surface 310 on the high tolerance face plate.

The thickness of the left outer flange 208 or right outer flange 308 or left outer tang 208 or right outer tang 308, left inner flange 108a or right inner flange 108b, and left inner tang 110a or right inner tang 110b may be varied to accommodate fatigue relief. As seen in fig. 3C, the outer flange forward

thickness

240, 340 expands into the rear

outer tang thickness

242, 342. Similarly, the anterior

inner flange thicknesses

140a, 140b expand into the posterior inner tang thicknesses 142a, 142 b.

The implementation provides a method 600 of engaging tension and compression members with a three-piece safety assurance clamp as shown in fig. 6. A central portion having a central top surface is received on a lower surface of the wing, step 602. The central portion has a left inner flange and a left inner tang having a first planar outer surface and a right inner flange and a right inner tang having a second planar outer surface oriented opposite the first outer surface.

A left side portion having a flat first inner surface received against the first outer surface and a left top surface coplanar with the central top surface to be received on a lower surface of the wing is connected with the left outer flange and the left outer tang adjacent the first outer surface using a first plurality of field fasteners, step 604.

Connecting a right side portion with the right outer flange and the right outer tang adjacent the second outer surface using a second plurality of field fasteners, the right side portion having a flat first inner surface received against the first outer surface and a right top surface coplanar with the central top surface to be received on the lower surface of the wing, step 606.

The first array of holes in the left inner flange of the left portion is concentrically aligned with the first array of mating holes in the left outer flange and the second array of holes in the right inner flange is concentrically aligned with the second array of mating holes in the right outer flange, step 608.

The third array of holes in the inside-left tang is concentrically aligned with the third array of mating holes in the outside-left tang and the fourth array of holes in the inside-right tang is concentrically aligned with the fourth array of mating holes in the outside-right tang, step 610.

The geometric arrangement of the first, second, third, and fourth mating hole arrays is configured to surround a potential propagating crack in either the left or right outer flange or in the left or right outer tang.

The geometric arrangement of the first, second, third, and fourth hole arrays is configured to surround a potential propagating crack in either the left or right inner flange or the left or right inner tang. The tension and compression members are received in the channels between the left and right inner tangs in the central portion, step 612.

The present disclosure includes, but is not limited to, example implementations according to the following clauses:

clause 1. a three-piece safety assurance clamp (20), the three-piece safety assurance clamp comprising:

a central portion (102) having a central top surface (104), a planar first outer surface (112), a planar second outer surface (114) oriented opposite the first outer surface, and a channel (118) configured to receive a tension and compression member (37);

a left side portion (202) connected adjacent to the first outer surface and having a flat first inner surface (209) received against the first outer surface and a left top surface (210) coplanar with the central top surface; and

a right side portion (302) connected adjacent the second outer surface and having a flat second inner surface (309) received against the second outer surface and a right top surface (310) coplanar with the central top surface.

Clause 2. the three-piece safety assurance clamp as defined in clause 1, wherein the central portion comprises:

a central top flange (104) having the central top surface; and

a body portion (106) having left and right inner flanges (108a, 108b) depending perpendicularly from the central top flange;

a left inner tang (110a) extending rearwardly from the left inner flange and a right inner tang (110b) extending rearwardly from the right inner flange;

wherein the left inner flange and the left inner tang collectively form the first outer planar surface and the right inner flange and the right inner tang collectively form the second outer planar surface.

Clause 3. the three-piece safety assurance clamp as defined in clause 2, wherein the left side portion comprises:

a left top flange (204) having the left top surface;

a left outer flange (206) depending perpendicularly from the left top flange; and

a left external tang (208) extending rearwardly from the left external flange, wherein the left external flange and the left external tang together form the planar first interior surface.

Clause 4. the three-piece security and safety clip as defined in clause 3, wherein the right side portion comprises:

a right top flange (304) having the right top surface;

a right outer flange (306) depending perpendicularly from the right top flange; and

a right external tang (308) extending rearwardly from the right external flange, wherein the right external flange and the right external tang together form the second planar interior surface.

Clause 5. the three-piece safety assurance clamp as defined in clause 4, wherein the central top flange has a first thickness (130), the left top flange has a second thickness (230), and the right top flange has a third thickness (330), the first, second, and third thicknesses being equal.

Clause 6. the three-piece safety assurance clamp as defined in clause 5, wherein the central top flange has a first plurality of holes (120) configured for a first plurality of fasteners (122a), the left top flange has a plurality of holes (220) for receiving a second plurality of fasteners (122b), and the right top flange has a third plurality of holes (320) for receiving a third plurality of fasteners (122c), wherein the first, second, and third plurality of fasteners have equal clamping lengths (123).

Clause 7. the three-piece safety assurance clamp as defined in any one of clauses 4 to 6, wherein,

a first array of holes (128a) in the left inner flange concentrically aligned with a first array of mating holes (228a) in the left outer flange;

a second array of holes (128b) in the right inner flange concentrically aligned with a second array of mating holes (328a) in the right outer flange;

a third array of holes (129a) in the left inner tang concentrically aligned with a third array of mating holes (229a) in the left outer tang; and is

A fourth array of holes (129b) in the inner right tang is concentrically aligned with a fourth array of mating holes (329b) in the outer right tang.

Clause 8. the three-piece safety assurance clamp as defined in clause 7, wherein,

the first array of holes, the first array of mating holes, the third array of holes, and the third array of mating holes receive a first plurality of field fasteners (124) to secure the left portion to the central portion; and is

The second array of holes, the second array of mating holes, the fourth array of holes, and the fourth array of mating holes receive a second plurality of field fasteners (126) to secure the right portion to the center portion.

Clause 9. the three-piece safety assurance clamp as defined in clause 8, wherein the geometric arrangement of the first, second, third, and fourth arrays of mating holes is configured to surround a potential propagating crack in either the left or right outer flanges, or the left or right outer tangs.

Clause 10. the three-piece safety assurance clamp as defined in clause 8, wherein the geometric arrangement of the first, second, third, and fourth arrays of holes is configured to surround a potential propagating crack in either the left or right inner flange or the left or right inner tang.

Clause 11 an aircraft (10) having a wing (12) with a system for operating flaps, the system comprising:

a plurality of flaps (14), each flap having a plurality of flap supports (16a, 16 b);

at least one actuator (22) supported in at least one flap support of the plurality of flap supports;

at least one carrier beam (30) for supporting one of the flaps, the carrier beam being rotatably engaged in at least one flap support rib (23);

a tension and compression link (37) coupled to the flap support rib:

a three-piece safety assurance clamp (20) connected to a lower surface (35) of the wing and having:

a central portion (102) having a central top surface (111) received on the lower surface, a flat first outer surface (112) and a flat second outer surface (114) oriented opposite the first outer surface, and a channel (118) configured to receive the tension and compression link (37);

a left side portion (202) connected adjacent the first outer surface and having a flat first inner surface (209) received against the first outer surface and a left top surface (210) coplanar with the central top surface and received on the lower surface; and

a right side portion (302) connected adjacent the second outer surface and having a flat second inner surface (309) received against the second outer surface and a right top surface (310) coplanar with the central top surface and received on the lower surface.

Clause 12. the aircraft as defined in clause 11, wherein the left side portion comprises:

a left top flange (204) having the left top surface;

Clause 13. the aircraft as defined in clause 12, wherein the right side portion comprises:

a right top flange (304) having the right top surface;

Clause 14. the aircraft as defined in clause 13, wherein the central top flange has a first thickness (130), the left top flange has a second thickness (230), and the right top flange has a third thickness (330), the first, second, and third thicknesses being equal.

Clause 15. the aircraft as defined in clause 14, wherein the central top flange has a first plurality of apertures (120) configured for a first plurality of fasteners (122a), the left top flange has a second plurality of apertures (220) for receiving a second plurality of fasteners (122b), and the right top flange has a third plurality of apertures (320) for receiving a third plurality of fasteners (122c), wherein the first, second, and third plurality of fasteners have equal clamping lengths (123) for connecting to the lower surface.

Clause 16. a method for engaging a tension and compression member with a three-piece safety assurance clamp, the method comprising:

receiving a central portion having a central top surface on a lower surface of a wing, the central portion having a left inner flange and a left inner tang having a flat first outer surface and a right inner flange and a left inner tang having a flat second outer surface, the second outer surface being oppositely oriented from the first outer surface;

connecting a left side portion with a left outer flange and a left outer tang adjacent the first outer surface using a first plurality of field fasteners, the left side portion having a flat first inner surface received against the first outer surface and a left top surface coplanar with the central top surface and received on the lower surface;

connecting a right side portion with a right outer flange and a right outer tang adjacent the second outer surface using a second plurality of field fasteners, the right side portion having a flat first inner surface received against the first outer surface and a right top surface coplanar with the central top surface and received on the lower surface; and

receiving the tension and compression member in a channel between the left inner tang and the right inner tang in the central portion.

Clause 17. the method as defined in clause 16, further comprising:

concentrically aligning a first array of holes in the left inner flange of a left portion with a first array of mating holes in the left outer flange; and

concentrically aligning a second array of holes in the right inner flange with a second array of mating holes in the right outer flange.

Clause 18. the method as defined in clause 17, further comprising:

concentrically aligning a third array of holes in the left inner tang with a third array of mating holes in the left outer tang; and

concentrically aligning a fourth array of holes in the inner right tang with a fourth array of mating holes in the outer right tang.

Clause 19. the method as defined in clause 18, further comprising:

geometrically arranging the first, second, third, and fourth arrays of mating holes around a potential propagating crack in the left or right outer flange, or in the left or right outer tang.

Clause 20. the method as defined in clause 19, further comprising: geometrically arranging the first, second, third, and fourth hole arrays around a potential propagating crack in either the left or right inner flange or the left or right inner tang.

Having now described various implementations in detail as required by the patent statutes, those skilled in the art will recognize modifications and substitutions to the specific implementations disclosed herein. Such modifications are within the scope and intent of the appended claims. In the description and claims, the terms "comprising," "incorporating," "including," "having," and "containing" are intended to be open-ended terms, and there may be additional or equivalent elements. The term "substantially" as used in the specification and claims means that the recited characteristic, parameter or value need not be achieved exactly, but that deviations or variations, including, for example, tolerances, measurement error, measurement accuracy limitations and other factors known to those skilled in the art, may occur in amounts that do not preclude the effect that the characteristic is intended to provide. As used herein, the terms "outside" and "inside" and "upper" and "lower" are used to describe relative positioning, and in addition to the specific implementations disclosed, may be replaced with appropriate descriptors, such as "first" and "second", "top" and "bottom" or "right" and "left", depending on the orientation of the actual implementation.

Claims

1. A three-piece safety assurance clamp (20), comprising:

a left side portion (202) connected adjacent the first outer surface and having a flat first inner surface (209) received against the first outer surface and a left top surface (210) coplanar with the central top surface; and

2. The three-piece safety assurance clamp of claim 1, wherein the central portion comprises:

a central top flange (104) having the central top surface; and

3. The three-piece security clip of claim 2, wherein the left portion comprises:

a left top flange (204) having the left top surface;

4. The three-piece safety assurance clamp of claim 3, wherein the right side portion comprises:

a right top flange (304) having the right top surface;

5. The three-piece safety assurance clamp of claim 4, wherein the center top flange has a first thickness (130), the left top flange has a second thickness (230), and the right top flange has a third thickness (330), the first, second, and third thicknesses being equal.

6. The three-piece safety assurance clamp of claim 5, wherein the central top flange has a first plurality of holes (120) configured for receiving a first plurality of fasteners (122a), the left top flange has a plurality of holes (220) for receiving a second plurality of fasteners (122b), and the right top flange has a third plurality of holes (320) for receiving a third plurality of fasteners (122c), wherein the first, second, and third plurality of fasteners have equal clamping lengths (123).

7. The three-piece safety assurance clamp of any one of claims 4 to 6,

8. The three-piece safety assurance clamp of claim 7, wherein,

9. The three-piece safety and security clip of claim 8, wherein the geometric arrangement of the first, second, third, and fourth arrays of mating holes is configured to surround a potential propagating crack in either the left or right outer flanges, or the left or right outer tangs.

10. The three-piece safety assurance clamp of claim 8, wherein the geometric arrangement of the first, second, third, and fourth hole arrays is configured to surround a potential propagating crack in either the inner left or right flange or the inner left or right tang.

11. An aircraft (10) having a wing (12) with a system for operating flaps, the system comprising:

a tension and compression link (37) coupled to the flap support rib;

12. The aircraft of claim 11, wherein the left portion comprises:

a left top flange (204) having the left top surface;

13. The aircraft of claim 12, wherein the right side portion comprises:

a right top flange (304) having the right top surface;

14. The aircraft of claim 13, wherein the central top flange has a first thickness (130), the left top flange has a second thickness (230), and the right top flange has a third thickness (330), the first, second, and third thicknesses being equal.

15. The aircraft of claim 14, wherein the central top flange has a first plurality of holes (120) configured to receive a first plurality of fasteners (122a), the left top flange has a second plurality of holes (220) to receive a second plurality of fasteners (122b), and the right top flange has a third plurality of holes (320) to receive a third plurality of fasteners (122c), wherein the first, second, and third plurality of fasteners have equal clamping lengths (123) for connecting to the lower surface.

16. A method for engaging a tension and compression member with a three-piece safety assurance clamp, the method comprising:

receiving a central portion having a central top surface on a lower surface of a wing, the central portion having a left inner flange and a left inner tang having a first planar outer surface and a right inner flange and a right inner tang having a second planar outer surface, the second outer surface being oppositely oriented from the first outer surface;

17. The method of claim 16, further comprising:

concentrically aligning a first array of holes in the left inner flange of the left portion with a first array of mating holes in the left outer flange; and

18. The method of claim 17, further comprising:

19. The method of claim 18, further comprising:

geometrically arranging the first, second, third, and fourth arrays of mating holes around a potential propagating crack in either the left or right outer flanges, or the left or right outer tangs.

20. The method of claim 19, further comprising: geometrically arranging the first, second, third, and fourth hole arrays around a potential propagating crack in either the left or right inner flange or the left or right inner tang.